典型飞机壁板结构的抗屈曲优化设计与试验验证

doi:10.7527/S1000-6893.2023.29679

Abstract

Abstract:

Stiffened panels are common load-bearing structures in aircraft fuselage and wings. Under axial compression and fuselage bending loads， they are susceptible to buckling failure， which limits the structural safety and aircraft service life. Empirical formula is often used for engineering calculations in aircraft structural static strength assessment. The engineering calculation of load-carrying capacity for stiffened panels is closely related to the selection of end support coefficients for fuselage frame structures. In the development of existing aircraft models， typically conservative end support coefficients are chosen， resulting in excessive structural safety margins and weight redundancies， hindering further advancements in aircraft lightweight design. To address the problem， this study first establishes a simulation calculation model for end support coefficients of typical aircraft panel structures based on slitting method， using Euler’s buckling theory. Subsequently， the coupled relationship between end support coefficients and the interaction between stiffened panel structures and supporting frame segments is analyzed in depth. Furthermore， the influence structural characteristic parameters such as frames and longitudinal stiffeners on end support coefficients is analyzed， and integrated buckling-resisting optimization designs of aircraft panel structure are conducted for frames， longitudinal stiffeners-skin， and frame-skin-longitudinal stiffener configurations. Finally， the effectiveness of buckling-resisting optimization designs for typical panel structure is validated through additive manufacturing of scaled-down specimens and axial compression tests. The established simulation and optimization methods in this study effectively enhance the buckling resistance of aircraft panel structures， offering significant opportunities for improving aircraft performances.

Key words: aircraft stiffened panel, buckling analysis, structural optimization, end support coefficient, critical buckling load

CLC Number:

V214.4

Liang MENG, Jinyuan YANG, Zhiwei YANG, Tong GAO, Hongquan LIU, Weihong ZHANG. Buckling⁃resisting optimization design of typical aircraft panel and test validation[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(5): 529679-529679.

Figures/Tables 22

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端部支持条件	端部支持系数
两端简支（S-S）	1.0
两端固支（E-E）	4.0
上端简支，下端固支（S-E）	2.04
上端自由，下端固支（F-E）	0.25

机型	机身壁板	机翼、尾翼壁板
ARJ21	2.0	1.3
某运输机	1.0	1.0
Ma700	1.5	1.2
EA	1.0	1.0

尺寸	设计变量	初始值	下限值	上限值
长桁上缘/mm	ZL1	8.00	4.00	10.00
长桁腹板/mm	ZL2	20.00	18.00	40.00
长桁下缘/mm	ZL3	10.00	8.00	14.00
长桁厚度/mm	ZT	2.00	1.20	2.80
蒙皮厚度/mm	T	3.00	1.50	3.50
框外缘/mm	KL1	10.00	9.00	14.00
框上缘/mm	KL2	21.00	16.00	25.00
框腹板/mm	KL3	70.00	60.00	80.00
框下缘/mm	KL4	10.00	9.00	15.00
框厚度/mm	KT	3.00	2.70	3.30

设计变量	初始值	优化点1	优化点2	优化点3
KL1/mm	10.00	13.90	13.92	13.86
KL2/mm	21.00	21.70	21.47	21.61
KL3/mm	70.00	61.89	61.96	61.26
KL4/mm	10.00	14.72	14.77	14.72
KT/mm	3.00	3.05	3.07	3.05
F_cr/N	12 016.00	12 085.00	12 085.00	12 085.00

设计变量	初始值	优化点1	优化点2	优化点3
ZL1/mm	8.00	9.69	9.80	9.67
ZL2/mm	20.00	39.74	39.56	39.73
ZL3/mm	10.00	8.51	8.18	9.95
ZT/mm	2.00	1.38	1.39	1.36
F_cr/N	12 016.00	37 169.00	37 041.00	36 631.00

Buckling⁃resisting optimization design of typical aircraft panel and test validation

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References 34

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设计变量	初始值	优化点1	优化点2	优化点3
ZL1/mm	8.00	7.14	7.16	7.38
ZL2/mm	20.00	39.97	39.96	39.97
ZL3/mm	10.00	13.86	13.78	13.78
ZT/mm	2.00	2.80	2.79	2.79
T/mm	3.00	2.28	2.28	2.27
F_cr/N	12 016.00	50 871.00	50 821.00	50 815.00

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